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(TGT) limit. The ATS will set engine thrust to this target without regard to engine operating
limits.
• ATS operation during take-off with thrust target (TGT) selected on FMS performance thrust
limit page is prohibited.
• ATS operation with maximum continuous thrust (MCT) selected as the FMS performance
thrust limit is prohibited.
• If both mode status displays (MSDs) fail, the crew must disengage the ATS and consider the
system inoperative.
• N1 thrust limit data is required and must be available from the FMS for ATS operation.
• The radio altimeter must be valid for the ATS retard mode operation. If radio altitude is
unavailable or invalid, the ATS must be disengaged prior to reaching 100 feet AGL.
• Use of the ATS during touch and go landings is prohibited. ATS must be disengaged if
system engages during touch and go landings.
• Use of the ATS during go-around is prohibited. Pilot must manually set thrust to override ATS.
ATS may be used to trim final N1, once manually set.
• If flaps are selected to less than 45° for landing, ATS must be disengaged prior to reaching
100 feet AGL.
LIMITATIONS
Power Plant
Vol. 1 02−05−3
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
6. AUTOMATIC PERFORMANCE RESERVE (APR)
If take-off performance is predicated upon the use of APR, the APR system must be verified
operative prior to take-off.
The APR system must be selected off, if an APR INOP caution message is displayed on EICAS.
APR OFF Performance must be used if an APR INOP caution message is displayed.
7. STARTER CRANKING LIMITS (GROUND AND AIR)
The starter must not be used if indicated N2 rpm exceeds 55%.
A. Engine Start
Normal engine start – Three consecutive engine start cycles with 5 minutes cooling between
additional cycles.
B. Associated Conditions
At initiation of thrust lever movement from SHUT OFF to IDLE:
(1) ITT must be 120°C or less for all ground starts.
(2) ITT must be 90°C or less for all air starts.
C. Dry Motoring Cycle
Dry motoring is performed with ignition OFF and thrust levers at SHUT OFF.
Dry motoring may be used for engine ground starts and engine airstarts.
START MAXIMUM TIME ON FOLLOWED BY
1 90 seconds 5 minutes off
2 and subsequent 30 seconds 5 minutes off
8. ENGINE RELIGHT
Engine starting in-flight is only permitted within the envelope defined in Figure 02−05−1:
LIMITATIONS
Power Plant
Vol. 1 02−05−4
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
8. ENGINE RELIGHT (CONT'D)
RELIGHT TYPE ENVELOPE (FIGURE 02–05–1)
Windmilling Altitude from 21,000 to 10,000 feet:
Airspeed from 300 to 348 KIAS, and from 12 to 55% N2.
Altitude from 10,000 to 8,000 feet:
Airspeed from 300 to 348 KIAS, and from 10 to 55% N2.
Altitude from sea level to 8,000 feet:
Airspeed 300 KIAS, and from 10 to 55% N2.
NOTE
N2 should be stable or increasing.
Starter-assisted Cross Bleed Altitude from 21,000 feet to 15,000 feet:
Airspeed from 200 KIAS up to 300 KIAS, and from 0 to 55% N2.
Altitude from 15,000 feet to sea level:
Airspeed from 140 KIAS up to 300 KIAS, and from 0 to 55% N2.
15
20
25
10
5
0
0 100
350
300
KIAS (KNOTS)
ALTITUDE X 1000 FT.
200
DFM0205_001
200
15,000 ft
21,000 ft 300 348
N2 >10%
W’MILL
N2 >12%
W’MILL
8,000 ft
STARTER
ASSISTED
10,000 ft
N2 >10%
Engine Air Start Envelope (In Flight)
Figure 02−05−1
LIMITATIONS
Power Plant
Vol. 1 02−05−5
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
9. FUEL
The maximum permissible fuel imbalance between the contents of the main left tank and the
main right tank is 182 kg (400 lb) for take-off and taxi.
The maximum permissible fuel imbalance between the contents of the main left tank and the
main right tank is 363 kg (800 lb) in flight.
The maximum permissible fuel imbalance between the contents of the main left tank and the
main right tank is 182 kg (400 lb) for landing.
Fuel remaining in a tank when the appropriate fuel quantity indicator reads zero is not usable.
Based upon a fuel density of 6.75 lb/US gallon, the maximum usable fuel load achieved by
pressure refueling for each tank is given below:
Left main tank 2,205 kg (4,860 lb)
Right main tank 2,205 kg (4,860 lb)
Auxiliary tank 3,251 kg (7,168 lb)
Tail tank 1,411 kg (3,112 lb)
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庞巴迪挑战者605机组操作手册 CL605-LIMITATIONS(6)
